U-passage gas turbine with turbulent heat transfer zone



y 1950 P. KOLLSMAN 2,514,875

U-PASSAGE GAS TURBINE WITH TURBULENT HEAT TRANSFER ZONE Filed Aug. 29,1945 s Sheets-Sheet 1 9401. KOLLSMA/V,

Arroe/ve'n Z I6' 3 my 1 INVENTOR.

July 11, 1950 P KOLLSMAN 2,514,875

U-PASSAGE GA S TURBINE WITH TURBULENT HEAT TRANSFER ZONE Filed Aug. 29,1945 3 Sheets-Sheet 3 N axe/me /YOZZL .Z I6. 6. 59

IN VEN TOR. R404 Kanspmu,

V [By Arron/vex Pmma July 11,1950

i v UNITED U-PASSAGE GAS TURBINE WITH TURBU- LENT HEAT TRANSFER- ZONEPaul Kollsman, New York, N. Y.

Application August 29, 1945, Serial No. 613,349

'1 Claims.

This invention relates to a thermodynamic engine for converting heatenergy into mechanical energy.

One object of the invention is the provision of a thermodynamic enginein which air or other gas is rotated to effect a compression-expansioncycle with the introduction of heat energy into the compressed gas, inwhich the rotational energy of the gas is imparted to the engine toclient its rotation.

Another object of the invention is the provision of a thermodynamicengine in which air or other gas is rotated to effect acompression-expansion cycle, with heat imparted to the compressed gas,with the rotational energy of the gasreturned to the engine to effectits rotation and with the gas collected and discharged through a jetnozzle to produce a reactive force.

-' with an annular diffuser through which the gas is discharged toconvert its rotational energy to assist the fiow of gas through thepath, and in which mechanical energy may be taken directly from therotating parts or in which the gas emerging from; the path may bedischarged through a jet nozzle to secure a reactive thrust.

Other objects and features of the invention will be readily apparent tothose'skilled in the art from the specification and appended drawingsillustrating certain preferred embodiments in which:

Figure 1 is a view partly in section and partly in elevation of anengine according to the present invention. t

Figure 2 is a partial elevational view of the engine.

Figure 3 is a vertical sectional view through the engine on planeIII-III of Figure 1.

Figure 4 is a view partly in vertical section and partly in elevation ofa modified form of the invention.

Figure 5 is a partial sectional view on the line V-V of .Figure 4.

Figure 6 is a view partly in vertical section and partly in elevation ofa further modification of the invention. l

1, and 3 there is provided a stationary exterior casing I having aforwardly extending cylindrical A portion 2 in which is supported aninterior, stationary, cylindrical portion 3 by means of spider legs 4.Within the cylindrical portion 3 is mounted a rotatable shaft 5 as bymeans of bearings 6 and I. Upon the forward end of shaft 5 is mounted arotor 8 of an electrical starting motor whose stator is indicated at 9and the wiring connection at H. Upon the inner end of the shaft 5 ismounted a rotor indicated generally at H and comprised ofsections l3 andil joined together in spaced relations to provide an insulating space I5therebetween. Adjacent to the axis of the rotor the space I5 is filledby an insulating seal Upon the sections l3 and II of the rotor l2 aremounted a plurality of circumferentially spaced, radially disposed finsl1 and I8 arranged in aligned relation so as to divide the space betweenthe rotor 12 and the interior walls of the casing I into a plurality ofindividual substantially U-shaped passages or chambers. The fins II haveaxially extending portions I9 directed toward the air inlet providedbetween the cylindrical portions 2 and 3 and about the cylindricalportion 3 is disposed a ring 2| carrying a plurality Figure '7 is apartial view on the line VIL-VII' of Figure 6.

In the form 01 the invention shown in of directional vanes 22 whichcurve in the direction of rotation of the rotor l2 and serve to directthe incoming gas to the passages between the fins II with a substantialtangential velocity. The inward ends of the fins l8 have axiallyextending portions 23 with the gas therebetween passing into a diffuserpassage 24 formed between parallel annular walls 25 and 25; the gaspassing from the outlet of diiiuser 24 into a collector 21 and beingthence discharged through a jet nozzle 28 to produce a reactive workingthrust.

Adjacent the bights of the U-shaped passages or chambers the casing l isprovided with double walls 29 and 3| having a space 32 therebetween forthe reception of a heating medium, here illustrated as gases ofcombustion from a burner nozzle 33 which are directed into the chamber32. The inner wall 29 is shown as a relatively thin section tofacilitate heat exchange and this wall is preferably formed of amaterial efiecting the transfer of heat with high efliciency. The heatexchange wall 23 extends not only around the bights of the U-shapedchambers but preferably for a distance along the legs of the passagesbetween fins II. The heating gases within chamber 32 are dischargedthrough outlet orifices 34. The legs of the passages or chambers betweenFigures 56 fins l1 and I. are of unequal length with the outangers 3 letleg between fins 58 extending the greater distance toward the axis ofthe rotor. A streamlined cap 35 is provided to reduce the air resistancewhich the elements in the cylindrical portion 3 would otherwise offer tomovement.

In the operation of the machine the rotor is initially brought up to aconsiderable speed by energizing the electric motor formed :by stator 9and rotor 8. Heat is supplied to the chamber 32 from the burner nozzle33 to heat the gases compressed adjacent to the periphery of the engine.The air or gas in the passages between fins l8 will be at a considerablyhigher temperature than that between fins I1 and the diiference indensity of the air in the columns and the'action of centrifugal forcethereon will effect a flow of air through the passages from the intakeportion ii! to the outlet portion 23. The incoming air will be directedwith a substantial tangential velocity by returned to the machine initsmovement inwardly toward the axis in the passage between the fins l8,but an additional rotational energy will Figures 6 and 7 is similar inits operation to that be imparted to the rotor by the greater length ofshaped passages. Theair emergingfrom the outlet of diffuser 24 passesinto the collector 21 and is finally discharged through the jet nozzle28 to 'provideareactive forward thrust.

In theform of-the invention illustrated in Figures 4 and 5the' engine isquite similar to that illustrated in Figures 1, 2, and 3 but themechanical energy is now taken from the machine from the rotor. shaft.Like parts in the machine have been given like reference numerals. Theprincipal changes in the machine of Figures 4 and 5 lie in. the omissionof the collector 21 and nozzle 38, the working extension of shaft 5, andthe change in the relative lengths of the legs of the U-shaped gas'passages. The rotatable shaft 5 is provided with an extension 30 towhich a power connection can bemade and the diffuser opening 24 isprovided between parallel annular walls 36 and 31 joined together byspaced pins 38 with the air from the difiuser outlet discharged into theatmosphere.

In the form of the invention of Figures 4 and 5 the legs of the passagesbetween fins l1 have been made considerably shorter than legs of thepassages of the machine of Figures 1, 2 and 3 to secure a greaterdifierence in length between the incoming and outgoing legs. In themachine of the Figures 1 through 3 it is desirable to have aconsiderable pressure energy in the gas passing into the collector 21with only suflicient rotational energy imparted to the rotor l2 toeffect its selfrotation at the high speeds of operation of the machine.

In the form of the invention of Figures 4 and 5 it is desired that thegas emerging from the diffuser 24 have little pressure energy and thatthe energy of the gas passing through the engine be delivered to therotor l2 in the form of rotational energy; therefore, the diflerenceinlength of the two legs of the U-shaped passages is made considerablygreater in the form of the invention of Figures 4 and 5 to secure thetransfer of the shown in Figures 4 and 5 and its-general constructionmay also be utilized with the collector and jet nozzle of Figures 1through 3. The engine shown in Figures 6 and 7 comprises an outer casing4| within which is mounted a rotatable shalt 42 on bearings 43 and 44.On shaft 42 is mounted a rotor 45 of an electric motor whose stator isindicated at 46 and the wiring connection thereto at 41. Upon shaft 42is mounted a rotor, indicated generally'at 48, and comprising a pair ofsections 49 and 5| mounted together in spaced relation to form aninsulating space 52 therebetween. Adjacent the axis of the engine thespace 52 is closed by a solid insulating seal 53. Upon sections 49 and5| of the rotor 48 are mounted circumferentially spaced, radiallydisposed fins 54 and 55 which are aligned to form a plurality ofindividual substantially U-shaped passages or chambers. About the rotorfins there is disposed a casing 56 formed of a material effectingtransfer of heat with high efiiciency, which casing is freely rotatableon the bearings 51 and 58 as a follower by air drag from the rotation ofthe air in the rotor chambers. Within casing l and about the peripheryand one side of. the casing 56 is disposed a stationary casing 59 intowhich are directed combustion gases from a burner nozzle 6! with thecombustion gases exhausted through an outlet 62. V I

For directing the incoming air or gas there are provided a plurality ofvanes 53 similar to vanes 22 of the forms of the invention shown inFigures 1 through 5, the vanes 63 also serving to mechanically supportthestationary portion containing bearing 43. Gas discharging from theengine from the passages between fins 55 passesthrough a difiuserpassage 64, formed by parallel annular walls in the casing, to an outlet55, from which they are exhausted to atmosphere in the case of an enginewhere mechanical energy is taken from the rotor shaft or from which theyare collected and discharged from a jet nozzle as shown in themodification of Figures 1 through 3. v

The operation of the engine of Figures 6 and 7 is similiar to thatpreviously described, the rotor 48 being initially brought up to aconsiderable speed by the electric motor and heat supplied from thechamber 59 through the walls of casing 55 to the compressed gas withinthe gas passages. Again the air flows through the gas passages by thediiference of density in the columns of the incoming and outgoing legsand the gas passing inwardly toward the axis between fins 55 returns itsrotational energy to the rotor 58. The outgoing legs of the gas passagesare again made longer than the incoming legs with resultant rotationalmechanical energy supplied to the rotor of the engine. The diffuser 64again serves to convert the rotational energy of the gas passingtherethrough to assist the normal fiow of air through the rotorpassages.

While the air or gas in the rotor passages in the forms of the inventionillustrated in Figures pretation within the claims.

1 through 5 is. rotated in-contact with a stationary casing, ln the formofthe invention shown in Figures ,6 andjl the casing", forming the outerboundary wall for the U-shaped passages, is free ito rotate as afollower to .the rotor ll which it will do at substantially one-halfspeed with a theoretical reduction in air frictional losses toone-fourth.

v While the legs of the gas passages have been referred to herein and inthe appended claims as being radial it will be understood that they mayi have any direction from the axis toward theperiphery which has aradial component.

While certain preferred embodiments of the invention have beenspecifically disclosed, it is understood that the invention is notlimited thereto, as many variations will be'readily ap-- parent tothoses skilled in the art and the invention is to be given its broadestpossible interterms of the following What is claimed is: l. A gasturbine comprising a stationary casing a rotor within said casing, saidrotor including i a; body and a plurality of circumferentially spaced acasing, constitute individual and separate U- shaped passages, the legsof the U extending substantially radially and the bight of the U lyingremote from the rotor axis, the two legs of. the passages being ofunequal length, the end of the shorter leg constituting an intake portand the end of the longer leg constituting an outlet port located closerto the axis than the inlet port, said blades constituting continuouschannel walls within the leg portions and the bight portion of saidpassages separating said passages from one another at the bight portion,and means associated with the casing for supplying heat to the U-shapedpassages, whereby gas passing through said passages and compressed bycentrifugal force is heated by transfer of heat from said casing withinthe area of greatest compression, the

heated gas expanding in its flow towards the discharge port transmittingenergy to the rotor, and a difluser adjacent said discharge passages.the

diffuser including lateral walls defining between them a space:progressively enlarging with the distance from the axis, the lateralwalls being substantially symmetrically arranged with respect to theoutward direction of the discharged gas.

4. A gas turbine as set forth in claim 3 in which member; a core memberwithin said outer memportion of the casing wall at the bight of saidport transmitting energy to the rotor.

2. A gas turbine as set forth in claim 1 in which the heat transferringwall portion of the casin extends with a greater area over said longerleg than it extends over the shorter leg of said pas- .sages.

3. A gas turbine comprising a casing, a rotor within said casing, saidrotor including a body and a plurality of circumferentially spacedsubstantially radially extending blades on said body, said bladestogether with said body defining a plurality of substantially U-shapedrotor channels which together with the interior wall of the casingconstitute U-shaped passages, the legs of the U extending substantiallyradially and the bight of the U lying remote from the rotor axis, thetwo legs of the passages being of unequal length, the end of the shorterleg constituting an intake port and the end of the longer legconstituting an outlet port located closer to the axis then the inletport, the said passages at the outlet port being of concave curvaturewith respect to the axis to discharge gas therefrom in a substantiallyradial outward direction, means associated with the casing for supplyingheat to the her, one of said members being rotatable relatively to theother about an axis, the other member being stationary, the interiorsurface of the outer member and the exterior surface of the inner memberproviding an interior space between them, the rotatable member beingprovided with a plurality of circumferentially spaced substantiallyradially extending blades subdividing theinterior space into a pluralityof substantially U-shaped'channels which together with the wall of thestationary member constitute individual and separate U-shaped passages,the legs of the U extending substantially radially and the bight of theU lying remote from the axis, the two legs of the passages being ofunequal length, the end of the shorter leg constituting an intake portand the end of the longer leg constituting an outlet port located closerto the axis than the inlet port, said blades constituting continuouschannel walls within the leg portions and the bight portion of saidpassages separating said passages from one another at the bight portion;and means associated with the stationary member for supplying heat tothe wall portion of the stationary member at the bight of the saidU-shaped passages, whereby gas passing through said passages andcompressed by centrifugal force at the bight is heated by transfer ofheat from said wall portion within the area of greatest compression,transfer of heat being promoted by the flow of gas within said passagesand also by the relative movement of said passages with respect to saidwall portion, the heated gas expanding in its flow towards the dischargeport and transferring energy to the blades of the rotating members.

6. A gas turbine comprising an outer enclosing member, a core memberwithin said outer member, one of said members being rotatable relativelyto the other about an axis, the other member being stationary, theinterior surface of the outer member and the exterior surface of theinner member providing an interior space between them, the rotatablemember being provided with a plurality of circumferentially spacedsubstantially radially extending blades, an intermediate casing withinsaid space mounted with freedom to spin about said axis, said bladessubdividing the space between the rotatable member and said intermediatecasing into a plurality of substantially U-shaped channels whichtogether with the wall of said intermediate casing constitute U-shapedpassages, the legs of the U- extending substantially radially and thebight of the U lying remote from the axis, the two legs of the passagesbeing of unequal length, the end of the shorter leg constiportion of thecasing wall at the bight of said tuting an intake port and the end ofthe longer leg constituting an loutlet port located closer to the axisthan ,the inletport; and meanstor supplying heat to the bight of saidU-shaped passages exterior ofsaidpassages, whereby gas pass- 8v throughsaid passages is heated within the passage portion within which the gasis under greatest compression, the heated gas expanding v in its flowtowards the discharge port and transmitting' energy to the rotor.

'7. A'gasturbine comprising a casing, a rotor "within said casing, saidrotor including a body and Ya plurality of circumferentially spaced subi'stantially radially extending blades on said body, said blades togetherwith said body defining a plurality of substantially U-shaped rotorchannels which together with the interior wall of the easing constituteU-shaped'passages, the legs of the U extending substantially radiallyand the bight of the Ulying remotefrom the rotor axis, the two legsofthe' passages being of unequal length, the

end of the shorter leg constituting an intake'port and the end of thelonger leg constituting an outlet port located closer to the axisthan'the inlet port. the body of the rotor comprising two portlons, oneportion being adjacent said shorter leg and the other portion beingadjacent the longer leg, said two portions being separated by an areahaving Poorer heat conductivity than the said 1 1 associated portions.and means with the casing 'for'supplying heatto the portion 01' the,casing REFERENCES CITED The following references are of record in themen: thispatent: I

. UNITED swim PATENTS Number Name Date 1,256,674 Fiittinger Feb.19, 19182,256,198 Hahn Sept. 16, 1941 2,272,676 Leduc -n; Feb. 10, 19422,283,176 Birmann May 19, 1942 2,334,625 Heppner Nov. 16, 1943 2,432,359Streid Dec. 9, 1947 OTHER nsmamcss Steam and Gas Turbines," by Dr. A.Stodola, translated by Dr. L. C. Loewenstein, McGraw-Hill Book Company,.New York, 1927, vol. II. p es 1220-1221.

